DE2935952A1 - ELECTRIC GENERATOR - Google Patents

Description

Applicant: Cecil R. Blomquist, Tacoma / USA Rodney L. O'Hiser, Portland / USA

Electric generator

The invention relates to an electrical generator and thus a device for generating electrical energy.

Electric generators are generally so-called field alternating current generators with a fixed stator and a rotating field structure or a rotor. Here the rotor is generally driven by gas, steam or a hydraulic turbine.

According to the invention, an electric generator is to be created, which by jet engines at or near the ends of blades is driven to which the rotor of the generator is attached. Furthermore, a generator should be the the type described above, in which the wings have ailerons to control the altitude of the wings, when rotated by the jet engines. Furthermore, control devices should be provided to the

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set upper and lower limit positions of the wings during operation so that when they flex, they would be carried, or if they should rise during the turning movement, such a lift through the upper one Position would be limited. Furthermore, an electric generator is to be created that is driven by jet engines which have thrust reinforcing devices, in which a quantity of liquid is evaporated with the help of unused engine heat, which in turn produces gases that create an extra boost. Finally, an electrical generator should be as described above Kind be created in which the rotor of a second electrical generator is driven by a stream of air generated by the jet engines and by the rotation of the blades on which the engines are attached are appropriate.

According to the invention this is achieved by a generator which uses a fixed, annular stator, which is mounted concentrically to an annular rotating rotor. The rotor is on to rotating horizontally Wings attached, which protrude from a central, rotatable hub and which are propelled by jet engines attached at or near the outer ends of the rotating blades. The position of each wing is determined by means of an aileron and is held between predetermined upper and lower limit positions, which are controlled by rolling are set, which abut upper and lower surfaces of an annular track that has the cross-section of a double-T-beam Has. In some embodiments of the invention, the thrust of the engines is improved by thrust boosters, which absorb some of the unused heat of the engines to evaporate a liquid and around it resulting gas exactly in the direction of the engine thrust.

In another embodiment of the invention, a two-

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Z $ J £ 935952

Ter electrical generator provided, with an annular stator attached to a circular foundation wall which runs vertically upwards and surrounds the outer ends of the rotating blades. In this embodiment of the invention, a number extend circumferentially in Spaced wind blades from a ring part upwards, which is in a groove in the upper surface the foundation wall is slidably supported. The rotor of the second generator is ring-shaped and on the wind blades and attached to the ring member so as to be spaced a certain distance from a surface of the stator. When the jet engines propel the blades around the rotatable hub, the resulting airflow causes the Wind blades and the rotor attached to them rotated in a direction which is opposite to the direction of rotation of the blades to thereby generate an alternating current in the stationary stator of the second generator.

According to the invention there is thus a device for generating created by electrical energy, in which an annular arrangement of rotor windings on a number of rotatable Wing is attached which extend outwardly from a central, rotatable hub. An annular, stationary one Arrangement of stator windings is arranged coaxially around the rotor. Through the jet engines that are on or attached near the outer ends of the vanes, the vanes and rotor are rotated and induced around the hub electrical energy in the form of alternating current in the stator windings. Some designs of electrical energy generating device have a second electrical generator, in which the stator on a stationary wall is attached, which surrounds the path of the rotating blades coaxially. A second annular rotor arrangement with wind blades, exposed to the airflow created by the jet engines and the rotation of the blades is sliding supported on the upper end of the stationary wall. When the jet engines propel the wings, the

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hey resulting airflow on the wind blades, creating the second The rotor is rotated and electric current is induced in the stator windings of the second electric generator.

The invention is described below on the basis of preferred embodiments described. Show it:

1 shows a schematic plan view of a Ge

generator according to the invention;

2 shows a sectional view through the generator of

Figure 1 along the line 2-2;

3 is an enlarged view of a wheel and

Track arrangement for supporting the blades of a generator according to the invention and for fixing the upper and lower limit positions of the rotating blades;

4 shows an enlarged schematic section

view of the exit side of a jet engine for driving the blades of the electric Generator of Fig.1, the sectional view along the line 4-4 of Fig.1 is made;

Fig.5 is a schematic plan view of a white

tere embodiment of the invention;

6 is a sectional view through the embodiment

shape of Fig.5 along the line 6-6 of the Fig. 5;

7 shows a schematic plan view of another

further embodiment of the invention, which a second electrical generator;

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Fig. 8

a sectional view through the embodiment of Figure 7 along the line 8-8 of Fig.7; and

FIG. 8 is an enlarged sectional view of the rotor and stator assembly of the embodiment of FIG Fig. 8.

In FIGS. 1 and 2, the electrical generator 10 according to FIG Invention a stationary stator 12, in which a rotor 14 is concentrically arranged. The rotor 14 is on one A pair of rotatable vanes 16 attached so that a surface of the rotor 14 is a predetermined distance from a surface of the stator 12 is arranged. When the vanes 16 rotate, the rotor 14 rotates in the stator 12 and induces electrical energy in the form of alternating current in the stator 12.

The rotor 14 is designed in exactly the same way as a conventional generator rotor, and is preferably of a kind that is more expansive or protruding rotor formed, which has a number of individually attached field poles 22, each on a annular core 26 are attached. The stator 12 is also designed in the same way as a conventional generator stator and is attached to a load-bearing surface 18, for example a concrete slab or other type of foundation. Further If the stator 12 has a number of windings or coils 20 which are arranged at the field poles 22 of the rotor 14 are.

The blades 16 are attached at their inner ends to a rotatable hub 28 which is rotatably supported about a support shaft 30 which is located in the center of the electric generator 10 and vertical from the supporting surface 18 protrudes upwards. The rotor 14 is attached to the underside of the blades 16 and further to the hub 28 by two additional ones Wing 32 attached, which is at a point that

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plus the circumference between the wings 16 is from which Hub 28 protrude radially outward. The wings are 16 propelled by jet engines 24 or by other propulsion devices which are attached to the outer ends of the blades 16 are mounted so aligned that a thrust is generated in a direction substantially perpendicular to the radial Axis of the wing 16 runs.

The hub 28 and the support shaft 30 are designed so that they represent a rotatable coupling through which fuel from a feed pipe 36 is fed, which passes through the interior of the support shaft 30 to fuel lines 38 which extend outwardly through the interior of the blades 16 and are connected to the jet engines 34. These rotatable coupling has in the support shaft 30 a circumferential groove 44 with a number of outlets which are in fluid communication stand with the supply pipe 36, which runs along the circumference the groove is arranged. The hub 28 has a number of circumferentially arranged collection inlets at the groove 44, so that during a rotary movement, fuel is delivered from the groove outlets to the hub inlets and thereby into the fuel lines 38 is directed. Similarly, a vaporizable liquid is supplied from a liquid supply line 50 from delivered through a second rotary coupling to fluid lines 52 which are routed over the interior of the blades 16 to to supply this liquid to a device which increases the thrust and which will be described in detail later.

The hub 28 and the shaft 30 are also used to collect electrical energy in the form of direct current from a stationary one to supply voltage source 54 mounted on support shaft 30 to rotating blades 16. The rotatable contact device for supplying direct current has a contact ring 56 which is in an insulated groove. 58 embedded which runs circumferentially around the shaft 30. Power is drawn by brushes 60 attached to each wing 16 are attached, and which are constantly attached to the ring 56

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gen when the blades 16 rotate. The stream from the outer Energy source 54 is used to generate the field poles magnetize (i.e. to supply the excitation current). To the others are supplied with electrical energy by the current to the jet engines 34 during the start-up period and with the power is also supplied to the control device for the wing position, which will be described below «

The wings 16 are in the rest position by a roller arrangement which generally includes a pair of wheels 62 attached to the lower end of support members 64 extending vertically downward from one side of each vane 16 at one between the stator 12 and the outer end the wing 16 protrude lying point. When the blades rotate, the wheels 62 run within the limits of a circular or ring-shaped path 66, which has a cross-section in the form of a double-T-beam, as shown in Figure 3 is. In particular, a lower surface 68 limits the wheels 62 in a lower position, for example when the Wing 16 are in the rest position. The upper surface 70 of the annular track 66 defines an upper limit position of the Height of the wings 16 fixed, so that the wings 16 should be raised enough during a rotary movement that Wheels 62 rest on surface 70 and move further upward the wing 16 prevent.

To maintain or control a vertical position of the wings between the upper and lower limit positions defined by track 66 and wheels 62, each wing 16 is provided with an aileron 72 and with a control device provided for actuating the ailerons 72 to adjust the altitude or the height of the wings 16 during a rotary movement to control. The ailerons 72 are designed in the same manner as the ailerons of conventional fixed-wing aircraft and have the task of increasing the buoyancy of the wings 16 change. The control device for the ailerons, which can be a conventional position sensing device 74, responds

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the angular position of the wings 16 with respect to the horizontal plane. In particular, a wing change around the The effect of the horizontal plane is that the control device 74 actuates a control motor 76 which is connected to the elevator 72 is coupled to change its position and to correct the wing lift angle.

As already stated above, the drive devices for rotating the blades are preferably jet engines 34 attached to the end of each wing 16; the engines 34 receive the fuel through the fuel lines 38. In order to further improve the efficiency of the jet engines 34, each of the engines can be equipped with a device which increases the thrust, which is a device for very rapid evaporation of a liquid which is supplied. As shown in Figure 4, Such thrust-increasing devices include a conical chamber 80, which in and the engine Exit side is attached. As shown in Figure 4, the chamber 80 has a closed tapered end 82, which is opposite the inlet side of the engine 24, and a partially closed end surface 84, which in the direction of of the engine outlet.

The conical chamber 80 is inside the engine 34 by means of four circumferentially spaced tubes 86 carried, which run between the wall of the chamber 80 and the engine casing 88. These pipes create you Passage for the liquid flowing from the fluid line 52 through the engine shroud 88 to the conical chamber 80 flows. The liquid supplied to the conical chamber 80 is vaporized by the intense heat which the chamber emits is exposed in the exit path of the engine 34. To continue the evaporation of the liquid in the chambers 80 To increase, each chamber can be provided with a heating coil 90, which is inside the chamber 80 at the closed End 82 is arranged. This heating coil is through over

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the current supplied to the brushes 60 is heated. Gases in the Kanuner 80 generated wetden are through the middle opening 92 in end face 84 so that the gases exiting chamber 80 are in substantially the same direction flow like the thrust-generating airflow that comes from the Engine 34 is delivered.

The operation of the jet engine will now be described Generator described; the jet engines 34 generate thrust to set the blades 16 in rapid rotation about the shaft 30. When the field poles 22 on the rotor rotate past the stator windings 20, electrical energy in the form of alternating current is fed into the Stator windings 20 are induced and connected to an output port for distribution through a conventional distribution system submitted.

The electrical output of the generator 20 can be varied within a wide range of performance by the Speed of the blades 16 is changed and a corresponding change in frequency is carried out at the stator output to a To generate an output with 60 or 50 Hz or, if necessary, another desired signal frequency. These changes in performance can be created by the generator by controlling the thrust of the jet engines works with essentially the same efficiency as the speed of rotation the rotor field poles 22 is adjusted accordingly with respect to the stator windings 30.

There is usually sufficient buoyancy during the turn on the wings 16 to raise them from the lower limit position in which the wheels 62 on the lower surface 68 the annular track 66 run. Such buoyancy is desirable so that the friction between the hub 28 and the Shaft 30 lower; / wirid and a friction between the wheels 6 2 and track 66 is omitted. During the operation of the generator

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tors 10 with different speeds are used to control the ailerons and their associated control devices Elevation of the wings 16 so that the wheels 62 do not rest against either the lower surface 68 or the upper surface 70 of the track 66. The upper surface 70 limits the wing lift to a predetermined upper position in the event that the ailerons 72 fail to effectively control wing lift.

Another embodiment of the invention is shown schematically in FIGS. Although it is a simple embodiment, it has, in modified form, all of the features of the generator 10 described above.

The generator in Fig.5 and 6 has eight radially extending Wing 100 with two upper and two lower jet engines 102 and 104, each attached to the end of each wing 100 are. Each jet engine 101 and 102 preferably has thrust-boosting devices of the type described above Kind on. In an embodiment of the invention, as shown in Fig.5 and 6, in which a relatively large number of jet engines is used, the thrust boosters are preferably used in a not shown On-board computer system used, which first indicates the electrical heating of the heating coils 90, and when the coils have been heated to the correct temperature, it initiates the supply of fluid to the booster chambers and controls the flow of fluid to increase the efficiency of the boosters to bring it to the maximum. Preferably, the four boosters that power the engines 102 and 104 of each wing 100 are assigned, operated one after the other by such an on-board computer.

The embodiment of Figures 5 and 6 also has an outer wall 110 on which vertically upwards from the load-bearing Surface 18 protrudes and coaxially surrounds the path which the outer ends of the blades 100 follow to during a high rev Generator operation leads to a tornado cyclone formation

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steer. The outer wall 110 has a series of ventilation openings 112 which are spaced apart from one another of the lower part of the wall 110 are arranged. The vents 112 have flaps or other devices for Controlling the volume and velocity of the air which passes through the vents 112 (as indicated by arrows 114 in Fig. 6) in order to supply the corresponding intake air for the engines 102 and 104.

In a further embodiment shown in FIGS. 7 to 9, the outer wall 110 in FIGS. 5 and 6 is through replaces a structure representing a second electrical generator to thereby generate electrical energy increase generated by the invention. In particular, the embodiment of FIGS. 7 and 8 has an upwardly projecting, annular foundation wall 120, which coaxially with an electrical generator of the type described above surrounds four blades 120, which are arranged perpendicular to one another and from the rotatable hub 28 and the shaft 30 protrude radially outward. A jet engine 124 is attached to the outer end of each wing 122, around the wings 122 drive in the manner described above. As with the previously described embodiments, there is a first electric generator by an annular rotor 14, which rotates with the blades 102, and by a stationary one Stator 12 is formed, which surrounds the rotor on the periphery. Furthermore, as already described above. Ailerons 72 are used to keep the wing attitude during operation of the electrical generator so that the wheels 62 do not touch either the upper or lower surfaces of the annular track 66. In the embodiment of Figure 7 and 8, the top surface 126 of the foundation wall 120 has a downwardly extending indentation or annular groove 127 which includes a rotatable ring member 128. By providing bearings 130 spaced from one another along the Side walls of the ring part 128 are arranged, and by bearings 132 which are between the lower end of the ring part 128 and

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the lower end of the groove 126 are arranged, the ring member 128 can slide freely in the groove 126. A number of rectangular ones Wind blades 124 extend vertically upward from the upper surface of the ring part 128 and are attached to support rods, those along the circumference at a distance from each other at the top Surface of the ring part 128 are arranged. The flat surfaces the wind vane 134 are relative to the impact of the airflow aligned, which is generated by the operation of the jet engines 124 and by the rotational movement of the blades 122 will. Further, the flat surfaces of the wind blades 134 can either be relatively flat and level or if necessary be profiled to create a maximum force on the wind blades.

In order to provide electrical energy, the second electrical generator has an annular stator 138 which runs along it of the upper edge of the foundation wall 120 by means of a number of support arms 140 arranged at a distance from one another on the circumference is supported, which the stator 138 slightly above the upper surface 126 bring the wall 120 into a predetermined position. An annular rotor 142 is on the bars supporting the wind blades arranged at a certain distance from the outer surface of the stator. The stator 138 and the rotor 142 are designed in the same way as the stator 12 and the rotor 14 of the above-described embodiment ^ shape in Figure 1 to 6; they indicate a number conventional windings, which form the field poles of the rotor, and the windings of the stator. As with the embodiments In FIGS. 1 to 6, electrical energy in the form of direct current is supplied to the rotor 142 by a device arranged in the ring part 120 A voltage source is supplied or electrical energy can be supplied in a similar manner to that described with reference to FIG a source provided outside of the ring part 128 via a slip ring and brush arrangement in the annular groove 126 are fed. The wall 120 has a series of air intake ducts for adequate air supply to the engines 124 144, which are arranged on the circumference along the lower part of the wall 120 at certain distances from one another. Required

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if necessary or necessary, the air inlet ducts 144 have flaps or other controls to control the amount of air going to the jet engines 124 and the blades 122 flows inward.

In operation, the blades 122 are rotated about the shaft 30 by the jet engines 124 so that alternating current is applied to the stator 12 is induced in the manner described above. At the same time bounce or hit the emerging from the jet engines Airflow and the airflow sweeping along the blades 122 on the upwardly protruding wind blades 134, whereby the ring member 128 rotated in the annular 126 in one direction which is opposite to the direction of rotation of the blades 122. When the ring member 128 rotates and the rotor 142 around the stationary stator 138 is moved, alternating current is induced in the stator windings, which have an output terminal and connected to a conventional power distribution system. As with the electrical generator, which includes the stator 12 and the Rotor 14 has, the frequency of the generated electrical energy is determined by the number of field poles and the stator windings as well as determined by the speed of the rotor. In those cases where a particular frequency is desired (i.e. usually electrical energy with 50 or 60 Hz), the energy distribution system can be a conventional device for frequency change or the foundation wall 120 and the ring member 128 can be rotated at a constant speed.

Energy can thus be saved with the invention. On the one hand, because the jet engines are far outside the axis of rotation of the Generators are arranged, the leverage of the wings is brought to a maximum. Since, on the other hand, the wings are given a lift, the frictional resistance between the hub 28 and the support shaft 30 is reduced to a minimum. Further the thrust booster in each jet engine increases the efficiency of the engines. Finally, through the use of the second electrical generator based on the embodiments has been described in Figures 7 and 8, the

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Force of the air / that of the jet engines and the wings flows away, used to generate additional electrical energy, thereby increasing the overall efficiency of the invention to increase.

End of description

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Claims (14)

Applicant: Cecil R. Blomquist, Tacoma / USA Rodney L. O'Hiser, Portland / USA Patent ρ back e M .J electrical generator characterized by a rotatable hub (28); by wings (16; 100; 122), attached to the hub (28) and protruding radially outward therefrom; by drive means (34; 102, 104; 124) attached to the wings (16; 100; 122) to generate thrust in one direction which is precisely runs perpendicular to the radial axis of the blades (16; 100; 122), so that the blades rotate about an axis of rotation through the rotatable hub (28); by a rotatable coupling device (44), which is mounted in the interior of the hub (28), to the drive devices (34; 102, 104; 124) Supply fuel; by a rotor (14) connected to the hub (28) for rotational movement, essentially is annular and coaxial with the rotatable hub (28); and by an annular, fixed stator (12), which is arranged coaxially at a predetermined distance from the rotor (14), so that by rotating the rotor (14) 030013/0719 electric current is generated in the stator (12). 2. Generator according to claim 1, characterized by an aileron attached to each of the wings (16; 122) and by a control device for operating the ailerons (72) _; to control the altitude and the lift of the wings (16; 122) during a turning movement. 3. Generator according to claim 1, characterized by the blades (16) attached to rollers (62) which the Carrying wings (16) in a lower limit position when the wings (16) are rotating at a speed lower than a predetermined speed to be turned around. 4. Generator according to claim 3, characterized in that that an annular track (66) below the rollers (62) has a lower bearing surface (68) and above the rollers (66) one has upper bearing surface (70), the rollers (66) on run on the lower surface (68) when the wings (16) are in their lower limit position and on the upper surface (70) abut the annular track (66) to thereby define a second limit position when due to the rotational movement of the vanes (16) the wings are lifted to a higher position. 5. Generator according to claim 4, characterized by at least one aileron (72) on each of the wings (16) and by a control device for operating the aileron (72) to keep the position of the wings (16) between the lower and upper limit position. 6. Generator according to claim 1, characterized by a rotatable contact arrangement (56, 58) for supplying electrical energy in the form of direct current to the rotor (14). 7. Generator according to claim 1, characterized in that that the propulsion device has a jet engine (34; 102, 104, 124). 030013/0719 8. Generator according to claim 1, characterized in that the drive device comprises a jet engine (24; 102, 104; 124) with a thrust-amplifying device with a chamber (80) which is arranged in the interior of the engine, heated by gases emerging from the engine and has an open end (84) directed towards the rear of the engine (34), and that the thrust-increasing device has a supply device (86) to supply a liquid to the chamber (80), in which the liquid evaporates and as a thrust-increasing device Gas is expelled which flows in substantially the same direction as the gas emerging from the engine (34). 9. Generator according to Anspurch 8, marked thereby e t that the chamber (80) is conical and attached to the outlet opening of the engine (34), and that the conical chamber (80) has a closed, pointed end (82) that is the intake side of the engine (84) is opposite, and has a partially closed end surface (84), one in the direction of the engine outlet pointing, central opening (92). 10. Generator according to claim 8, characterized by a selectively heatable coil (90) in the chamber (80) to evaporate the liquid more quickly that the chamber (80) is supplied. 11. Generator according to claim 1, characterized in that an upwardly projecting, annular Foundation wall (120) surrounds the hub (28) coaxially, is arranged outside the outer end of the blades (122) and a Groove (127) in its upper surface (126) that a Ring part (128) is slidably disposed in the groove (127) of the foundation wall (120); that a number upwards above The wind blade (134) is circumferentially arranged at predetermined intervals above the upper surface (126) of the ring part (128), each of the blades (134) being aligned accordingly 030013/071 « is to the arising during the operation of the drive device Air flow and the air flowing away from the blades (122) during their rotational movement, so that the ring part (128) rotates in the groove (127) in a direction opposite to the direction of rotation of the vanes (122); that a second annular rotor (142) is firmly connected to the wind blades (134) and the ring part (128), the second rotor (142) is arranged coaxially with respect to the rotatable hub (28), and that a second annular, fixed stator (138) is coaxial to the second rotor (142) is arranged, wherein a surface of the second rotor (142) at a distance of one Surface of the second stator (138) is arranged so that the second rotor (142) induces alternating current in the second stator (138), when the ring member (128) and the wind blades (134) are rotated will. 12. Generator according to claim 11, characterized in that that air inlet openings (144) along the circumference of the Foundation wall are arranged to supply the drive device (124) with an air flow. 13. Generator according to claim 11, characterized in that that the propulsion device comprises one or more jet engines (124) attached to the wings (122), and that the jet engines (124) are thrust-increasing devices with a chamber (80) which is in the one with a high temperature outflowing gas of the engine (124) is arranged, and is provided with a supply device to feed a liquid into directing the interior of the chamber (80) which has an open end facing the rear of the engine (124), to use the outflowing gases to vaporize the liquid in the chamber (80). 14. Generator according to claim 11, characterized by the means controlling the altitude to the location to maintain the wing (122) between an upper and a lower limit position, which control the altitude 030013/071 * de means at least one attached to each of the wings (122) Ailerons (72) has to change the resulting lift when the wings (122) are rotated, by wheels (62) protruding vertically downward from the blades (122) through a track (66) connecting the rotatable hub (28) coaxially surrounds a location located between the rotatable hub (28) and the outer wall, the track (66) being a upper support surface (70) for the wheels (62) to the upper Define limit position, and a lower support surface (68) for the wheels (62) for establishing the lower limit position and by a means controlling the aileron which is operative is connected to the ailerons (72) to bring each of the ailerons (72) into a corresponding position to thereby holding the wings (122) between the upper and lower limit positions. 030013/071 *